Numerical Study Of Battle Damaged
Two-dimensional Wings
Author(s)
S. Djellal, T. Azzam, M. Djellab & K. Lakkaichi
Abstract
The flow around a NACA 641-412 airfoil with circle damage is numerically
investigated using the Ansys Fluent package. Several diameter values are
considered for the damage which is located at either quarter or mid chord. The
numerical domain is covered with a multiblock structured hexagonal grid
consisting of 344,680 cells in the undamaged case and 351,540 cells in the
damaged case. Inside the damage hole, a structured tetragonal mesh is used.
Turbulence effects are taken into account via the k- model. The results show
that the presence of the damage hole decreases the lift coefficient and increases
the drag coefficient, resulting in a loss of airfoil performance (fineness decrease).
The numerical simulations show that the flow through the damage corresponds
either to a weak or a strong jet. In the first case an attached wake forms giving
the smallest change in the force coefficients whereas the second case shows a
separated wake with a reverse flow giving the highest force coefficient change.
The present paper also compares the structure of the damage through flow with
previously published experimental results. Finally, the numerical solution is
qualitatively and quantitatively validated using available experimental results.
Keywords: damage, drag, lift, strong jet, weak jet, undamaged.
1 Introduction
The survivability of an aircraft is becoming one of the key aircraft design
requirements [1] and is dependant upon its vulnerability to damage caused by a
variety of threats. Published works to date in this field focus mainly on twodimensional
wings.
Keywords
damage, drag, lift, strong jet, weak jet, undamaged.
Related Book
Other papers in this volume
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